Adhoc geo-fiducial mats for landing UAVs

ABSTRACT

An apparatus for visual navigation of a UAV includes a geo-fiducial mat and a plurality of geo-fiducials. The geo-fiducial mat includes a landing pad region that provides a location for aligning with a landing pad of a UAV and a survey point. The geo-fiducials are each specified for a unique directional and offset position in or about the landing pad region relative to the survey point. The geo-fiducials each includes a two-dimensional (2D) pattern that visually conveys an alphanumerical code. The 2D pattern has a shape from which a visual navigation system of the UAV can visually triangulate a position of the UAV.

TECHNICAL FIELD

This disclosure relates generally to unmanned aerial vehicles (UAVs),and in particular but not exclusively, relates to visual navigation andlanding pads for UAVs.

BACKGROUND INFORMATION

A UAV is a vehicle capable of air travel without a physically-presenthuman operator. UAVs may be provisioned to perform various differentmissions, including payload delivery, exploration/reconnaissance,imaging, public safety, surveillance, or otherwise. The missiondefinition will often dictate a type of specialized equipment and/orconfiguration of the unmanned vehicle.

Safe and efficient UAV navigation relies upon the UAV having an accurateand precise navigation solution (for example, a latitude, longitude, andaltitude). For example, a UAV may rely on a global positioning system(GPS) to generate a navigation solution in wide open environments;however, GPS navigation may lack the precision necessary to navigate aUAV in confined or crowded environments (such as an indoor UAV basehaving numerous UAVs). In addition, weather and other contingencies maydegrade GPS signal strength, which may compromise the ability of a UAVto generate an accurate navigation solution by GPS. Some environmentsmay experience degraded GPS performance, for example due to multipath,and others may be completely GPS-denied, i.e., may lack GPS signalaltogether. These are merely exemplary scenarios, as other challengescharacterize UAV navigation. Ultimately, the ability to generate areliable, accurate, and precise navigation solution is important toefficient and safe UAV navigation.

BRIEF DESCRIPTION OF THE DRAWINGS

Non-limiting and non-exhaustive embodiments of the invention aredescribed with reference to the following figures, wherein likereference numerals refer to like parts throughout the various viewsunless otherwise specified. Not all instances of an element arenecessarily labeled so as not to clutter the drawings where appropriate.The drawings are not necessarily to scale, emphasis instead being placedupon illustrating the principles being described.

FIG. 1 illustrates a system for visual navigation of an unmanned aerialvehicle (UAV) during landing or takeoff using a geo-fiducial mat, inaccordance with an embodiment of the disclosure.

FIG. 2A illustrates a geo-fiducial mat including mid-sized and largegeo-fiducials, in accordance with an embodiment of the disclosure.

FIG. 2B illustrates a landing pad that is to be aligned with a landingpad region on the geo-fiducial mat, in accordance with an embodiment ofthe disclosure.

FIG. 2C illustrates small geo-fiducials for adhering to, or positioningadjacent to, the landing pad, in accordance with an embodiment of thedisclosure.

FIG. 3A illustrates a geo-fiducial mat including only mid-sizedgeo-fiducials, in accordance with an embodiment of the disclosure.

FIG. 3B illustrates a geo-fiducial mat used with only small-sizedgeo-fiducials, in accordance with an embodiment of the disclosure.

FIG. 3C illustrates a combo geo-fiducial mat including multiple landingpad regions having geo-fiducial referenced from a single survey point,in accordance with an embodiment of the disclosure.

FIGS. 4A and 4B illustrate perspective and underside views of ademonstrative UAV capable of navigating via a GPS signal or opticaltriangulation using geo-fiducials, in accordance with an embodiment ofthe disclosure.

FIG. 5 is a flow chart illustrating a process for using adhocgeo-fiducials on a geo-fiducial mat to navigate a takeoff, in accordancewith an embodiment of the disclosure.

FIG. 6 is a chart illustrating an example geo-fiducial map includingentries populated for both regular and adhoc geo-fiducials, inaccordance with an embodiment of the disclosure.

DETAILED DESCRIPTION

Embodiments of a system, apparatus, and method for visual navigation ofan unmanned aerial vehicle (UAV) are described herein. In the followingdescription numerous specific details are set forth to provide athorough understanding of the embodiments. One skilled in the relevantart will recognize, however, that the techniques described herein can bepracticed without one or more of the specific details, or with othermethods, components, materials, etc. In other instances, well-knownstructures, materials, or operations are not shown or described indetail to avoid obscuring certain aspects.

Reference throughout this specification to “one embodiment” or “anembodiment” means that a particular feature, structure, orcharacteristic described in connection with the embodiment is includedin at least one embodiment of the present invention. Thus, theappearances of the phrases “in one embodiment” or “in an embodiment” invarious places throughout this specification are not necessarily allreferring to the same embodiment. Furthermore, the particular features,structures, or characteristics may be combined in any suitable manner inone or more embodiments.

Embodiments described herein provide a quick and efficient adhoctechnique for deploying a visual navigation system for UAVs. Thetechnique is particularly well suited for rapid deployment of landingpads where more precise navigation is needed than is currently availablefrom the civilian global positioning system (GPS). The techniquepositions multiple geo-fiducials about a landing pad, but only requiresa survey of a single point. The multiple geo-fiducials are each deployedabout a landing pad region at specified unique directional and offsetpositions relative to the survey point. Some geo-fiducials may bedisposed on or adhered to the landing pads themselves. Some or all ofthe geo-fiducials may be integrated into a geo-fiducial mat that isquickly deployable and easily aligned with a landing pad, which may alsofunction as a charging pad for the UAV. The geo-fiducial mat may berolled, folded, or assembled similar to puzzle pieces to provide easytransport and quick deployment. The geo-fiducials are two-dimensional(2D) patterns that may be used for visual triangulation and which eachvisually convey an alphanumerical code for uniquely identifying thespecific geo-fiducial. A pad identification associated with the landingpad informs the UAV that the geo-fiducials are adhoc, which triggers theUAV to compute the individual locations of each geo-fiducial based uponthe location information of the single survey point and the uniquedirectional and offset position specified for each geo-fiducial. Thelocations are then populated into the UAV's geo-fiducial map. Theaddition of the adhoc geo-fiducials into the geo-fiducial map may occurupon initial takeoff from the landing pad. However, this technique maybe used for adding any number or type of geo-fiducials at a variety ofdifferent times.

FIG. 1 illustrates a system 100 for visual navigation of a UAV duringlandings, takeoffs, or close-in navigation using a geo-fiducial mat, inaccordance with an embodiment of the disclosure. The illustratedembodiment of system 100 includes a UAV 105 having an optical navigationsystem, a geo-fiducial mat 110, a plurality of geo-fiducials xx0 throughxx9, and a landing pad 9 xx. FIG. 2A-2C illustrate the components ofsystem 100 separated from each other. For example, FIG. 2A illustratesjust geo-fiducial mat 110, FIG. 2B illustrates just landing pad 9 xx,and FIG. 2C illustrates just geo-fiducials xx0-xx3.

Referring to FIG. 2A, the illustrated embodiment of geo-fiducial map 110includes the following components integrated thereon: mid-sizedgeo-fiducials xx4-xx7, large geo-fiducials xx8 and xx9, a survey point205, alignment markings 210 defining a landing pad region 211, adirectional marker 215, and hold-down points 220. As illustrated in FIG.1, landing pad 9 xx is placed on geo-fiducial mat 110 and aligned byalignment markings 210. Small geo-fiducials xx0-xx3 are adhered to orotherwise disposed on landing pad 9 xx. Small geo-fiducials xx0-xx3 mayalso be positioned on (or integrated with) geo-fiducial mat 110immediately adjacent to landing pad region 210.

Geo-fiducials xx0-xx9 are 2D patterns having a shape from which anoptical navigation system of UAV 105 can visually triangulate itsposition. For example, the geo-fiducials may be composed of a highcontrast pattern (e.g., black and white rectangular pixels) formed intoan overall rectangular or square shape. The corners of the overall shapeof each 2D pattern may be referenced by the optical navigation system totriangulate a position of UAV 105. To improve visibility, eachgeo-fiducial may be outlined with a white border and geo-fiducial mat110 may otherwise be colored with a mid-level shade of grey. Forexample, if a greyscale value of 0 is associated with white and agreyscale value of 100 is associated with black, then geo-fiducial mat110 may generally be colored with a grey scale value of approximately50.

In the illustrated embodiment, geo-fiducials are provided in threedifferent sizes small (xx0-xx3), medium (xx4-xx7), and large (xx8 andxx9). The illustrated geo-fiducials are positioned at four differentcorners or along four different sides of landing pad region 211. In oneembodiment, the small geo-fiducials are approximately 16.3 cm square insize and positioned closest to the center of landing pad region 211. Ofcourse, other sizes (e.g., 24.3 cm square) may be implemented. In theillustrated embodiment, the small geo-fiducials are adhered to orotherwise disposed on landing pad 9 xx in its four corners. In otherembodiments, the small geo-fiducials may be centered along the foursides of landing pad 9 xx or even positioned on or integrated intogeo-fiducial mat 110 immediately adjacent to landing pad 9 xx as opposedto being disposed on landing pad 9 xx. Due to their closest proximity tothe center of landing pad region 211 and their small size, the smallgeo-fiducials are the first geo-fiducials seen by UAV 105 upon initialtakeoff and the geo-fiducials used for navigation at close in distances.They provide close-in navigation for precise landing on landing pad 9xx.

The medium geo-fiducials xx4-xx7 are larger than the small geo-fiducialsand positioned further away from the center of landing pad region 211than the small geo-fiducials. In one embodiment, the mediumgeo-fiducials are approximately 32.6 cm square in size. Of course, othersizes (e.g., 48.6 cm square) may be implemented. In the illustratedembodiment, four medium geo-fiducials are each aligned with themid-point of a corresponding side of the rectangular landing pad region211. The medium geo-fiducials provide intermediate range navigation toUAV 105 and can be seen by the optical navigation system of UAV 105 fromrelative higher altitudes than the small geo-fiducials.

The large geo-fiducials xx8-xx9 are larger than the small and mediumgeo-fiducials and positioned further away from the center of landing padregion 211 than the small and medium geo-fiducials. In one embodiment,the large geo-fiducials are approximately 81.8 cm square in size. Ofcourse, other sizes (e.g., 122 cm square) may be implemented. In theillustrated embodiment, two large geo-fiducials are positioned onopposing sides of landing pad region 211 and aligned with a mid-point ofthe sides of the rectangular landing pad region 211. The largegeo-fiducials provide high altitude navigation to UAV 105 and can beseen by the optical navigation system of UAV 105 from relative higheraltitudes than the small or medium geo-fiducials. Other numbers,combinations, sizes, and positions of small, medium, and largegeo-fiducials may be implemented.

The 2D pattern of each geo-fiducial visually conveys an alphanumericalcode. In one embodiment, the 2D pattern is similar to a quick response(QR) code, though other types of visual codes may be used. Thealphanumerical code may be strictly numbers, strictly letters,characters, or symbols, or any combination of all of these. In theillustrated embodiment, the alphanumerical code of each geo-fiducials isa three-digit number, though shorter or longer codes may be used. In theillustrated embodiment (see FIGS. 2A-C), the alphanumerical codeconveyed by each of the geo-fiducials shares a common first portion 225that is associated with a pad identification of landing pad 9 xx anddifferent second portion 230 that individually distinguishes each of thegeo-fiducials associated with a given geo-fiducial mat 110 from eachother. Similarly, the pad identification (e.g., 9 xx) includes a firstsegment 235 having a value (e.g., ‘9’) indicating that the geo-fiducialsassociated with geo-fiducial mat 110 are not individually surveyed, butrather locations of geo-fiducials xx0-xx9 associated with geo-fiducialmat 110 are computable based upon location information of survey point205 and the pre-specified unique directional and offset position of eachof the geo-fiducials. Accordingly, the geo-fiducials are each calculatedas directional offsets from the single surveyed point. The value offirst segment 235 indicates whether the associated geo-fiducials are“adhoc” requiring computation. The illustrated embodiment reserves thevalue ‘9’ for indicating adhoc, but of course, other values may be used.In particular, other values may be reserved to designate different typesof geo-fiducial mats having different numbers of geo-fiducials indifferent configurations (e.g., directional and offset positions,fiducial sizes, etc.). For example, geo-fiducial mat 315 (see FIG. 3C)may be designated with a value of “11” while the geo-fiducial mat 300(see FIG. 3A) may be designated with a value of “12”, etc. The secondsegment 240 of the pad identification matches the common first portion225 of the alphanumerical codes to provide association of thegeo-fiducials to a given geo-fiducial mat 110, and in particular,association with the location information of survey point 205. In otherembodiments, the order of the segments 235 and 240 or the order of thecommon and different portions 225 and 230 may be switched up.

In addition to integrated geo-fiducials, geo-fiducial mat 110 includes anumber of other integrated features. For example, geo-fiducial mat 110includes a marking indicating survey point 205. Survey point 205provides the precise location for a field technician to survey. In theillustrated embodiment, survey point 205 is located in the center oflanding pad region 201; however, survey point 205 may be locatedanywhere on geo-fiducial mat 110.

Another feature disposed on geo-fiducial mat 110 includes directionalmarker 215 for aligning geo-fiducial mat 110 with a predetermineddirection. The directional marker 215 provides a simple visual guide tothe field technician when deploying a new geo-fiducial mat 110. Byaligning geo-fiducial mat 110 with the predetermined direction (e.g.,magnetic north), the absolute positions of the geo-fiducials aredeterminable based upon the location information of the single surveypoint 205 and the unique directional and offset position specified foreach of the geo-fiducials relative to survey point 205. The uniquedirectional and offset positions are predetermined or known values.

Yet another feature of geo-fiducial mat 110 includes alignment markings210. Alignment markings 210 are disposed on geo-fiducial mat 110 toindicate the landing pad region 211 and aid accurate alignment oflanding pad 9 xx to landing pad region 211. In the illustratedembodiment, alignment markings 210 define two different sizes forlanding pad region 211 to facilitate accurate alignment of multipledifferent landing pads to geo-fiducial mat 110. Although FIG. 2Aillustrates the use of right angle corner markings to define therectangular shaped region of landing pad region 211, other markings maybe used.

In one embodiment, geo-fiducial mat 110 is fabricated of a flexiblesubstrate material that is amenable to rolling or folding.Alternatively, geo-fiducial mat 110 may be fabricated of more rigid orfirm sections that can be disassembled into separable sections like apuzzle (e.g., see FIG. 3B). These rolling, folding, or separableimplementations facilitate easy transport and deployment to remote ortemporary locations. Geo-fiducial mat 110 may also include hold-downpoints 220 disposed about the perimeter to secure geo-fiducial mat 110to the ground and ensure that wind or other environmental factors do notinadvertently move the mat. In the illustrated embodiment, hold-downpoints 220 are grommet holes that may be spiked or tied in location.

FIG. 2A illustrates just one example configuration for deploying small,medium, and large geo-fiducials with geo-fiducial mat 110. FIGS. 3A-3Cillustrate three other example configurations. These threeconfigurations are not intended to be limiting, but rather merelydemonstrative examples. FIG. 3A illustrates a geo-fiducial mat 300including only mid-sized geo-fiducials xx4-xx7 integrated onto the matwhile omitting the larger geo-fiducials. FIG. 3A illustrates fourgeo-fiducials, one disposed on each side of landing pad region 211. Theuse of multiple geo-fiducials on different sides of landing pad region211 provides improved tolerance/robustness against environmental factorssuch as glare, shadows, etc. However, it should be appreciated thatfewer than four mid-sized geo-fiducials may be used. For example, threemid-sized geo-fiducials may provide sufficient environmental robustnessas well.

FIG. 3B illustrates a geo-fiducial mat 305 used with only smallgeo-fiducials xx0-xx3 disposed on landing pad 9 xx. In the illustratedembodiment, geo-fiducial mat 305 does not include any integratedgeo-fiducials; however, in another embodiment, one or more of smallgeo-fiducials xx0-xx3 may be integrated onto geo-fiducial mat 305immediately adjacent to the landing pad region. FIG. 3B illustrates foursmall geo-fiducials, one disposed at each corner of landing pad 9 xx.Similar, as mentioned above, it should be appreciated that fewer thanfour small geo-fiducials may be used. For example, three smallgeo-fiducials positioned in only three corners or along three sides mayprovide sufficient environmental robustness as well. FIG. 3B alsoillustrates how geo-fiducial mat 305 may be segmented into sections310A-D, which are separable like a puzzle for easy transport anddeployment. Although FIG. 3B illustrates just four sections 310, more orless separable sections may be implemented. The separation interfacebetween each section need not undulate as demonstratively illustrated.

FIG. 3C illustrates a combo geo-fiducial mat 315 including multiplelanding pad regions 320A and 320B having geo-fiducial referenced from asingle survey point 325, in accordance with an embodiment of thedisclosure. As illustrated, a single geo-fiducial mat 315 with a singlesurvey point 325 can be deployed to service multiple landing pads 9 xxand 9 xy. Geo-fiducial mat 315 facilitates quick deployments of fleetsof UAVs. Although FIG. 3C illustrates, just two landing pads sharing asingle geo-fiducial mat, in other embodiments, geo-fiducial mats thatcan accommodate more than two landing pads are envisioned.

FIGS. 4A and 4B illustrate perspective and underside views of ademonstrative UAV 400 capable of navigating via optical triangulationusing geo-fiducials, in accordance with an embodiment of the disclosure.UAV 400 is one possible implementation of UAV 105. The illustratedembodiment of UAV 400 is a vertical takeoff and landing (VTOL) UAV thatincludes separate propulsion units 406 and 412 for providing horizontaland vertical propulsion, respectively. UAV 400 is a fixed-wing aerialvehicle, which as the name implies, has a wing assembly 402 that cangenerate lift based on the wing shape and the vehicle's forward airspeedwhen propelled horizontally by propulsion units 406. FIG. 4A is aperspective top view illustration of UAV 400 while FIG. 4B is a bottomside plan view illustration of the same.

The illustrated embodiment of UAV 400 includes a fuselage 404. In oneembodiment, fuselage 404 is modular and includes a battery module, anavionics module, and a mission payload module. The battery moduleincludes a cavity for housing one or more batteries for powering aerialvehicle 400. The avionics module houses flight control circuitry ofaerial vehicle 400, which may include a controller 450 (e.g., processorand memory), communication electronics and antennas (e.g., cellulartransceiver, wife transceiver, etc.), an optical navigation system 455,and various sensors (e.g., global positioning sensor 460, an inertialmeasurement unit (IMU), a magnetic compass, etc.). The opticalnavigation system 455 may include one or more cameras, such as aforward-facing camera 465 and downward facing camera 470 foridentifying, reading, and triangulating geo-fiducials. The missionpayload module houses equipment associated with a mission of aerialvehicle 400. For example, the mission payload module may include apayload actuator for holding and releasing an externally attachedpayload. In another embodiment, the mission payload module may include acamera/sensor equipment holder for carrying camera/sensor equipment(e.g., camera, lenses, radar, lidar, pollution monitoring sensors,weather monitoring sensors, etc.).

The illustrated embodiment of UAV 400 further includes horizontalpropulsion units 406 positioned on wing assembly 402, which can eachinclude a motor, shaft, motor mount, and propeller, for propelling UAV400. The illustrated embodiment of UAV 400 includes two boom assemblies410 that secure to wing assembly 402. In one embodiment, wing assembly402 includes a wing spar (not illustrated) disposed within a wing foilof wing assembly 402. The wing spar may be a hollow structural member(e.g., tubular rod) extending along the internal length of the wing foiland provides a main structural member that connects wing assembly 402 tofuselage 404 and to which boom assemblies 410 mount.

The illustrated embodiments of boom assemblies 410 each include a boomhousing 411 in which a boom spar (not illustrated) is disposed, verticalpropulsion units 412, printed circuit boards 413, and stabilizers 408.Boom spars may also be hollow structural members (e.g., tubular rods)that provide the main structural support to which the wing spar andvertical propulsion units 412 are mounted. The boom spars are alsoreferred to as “boom carriers” since they carry the load forces on boomassemblies 410. Vertical propulsion units 412 can each include a motor,shaft, motor mounts, and propeller, for providing vertical propulsion.Vertical propulsion units 412 may be used during a hover mode where UAV400 is descending (e.g., to a landing pad) or ascending (e.g., takeofffrom a landing pad). Stabilizers 408 (or fins) may be included with UAV400 to stabilize the UAV's yaw (left or right turns) during flight.

During flight, UAV 400 may control the direction and/or speed of itsmovement by controlling its pitch, roll, yaw, and/or altitude. Forexample, the stabilizers 408 may include one or more rudders 408 a forcontrolling the UAV's yaw, and wing assembly 402 may include elevatorsfor controlling the UAV's pitch and/or ailerons 402 a for controllingthe UAV's roll. As another example, increasing or decreasing the speedof all the propellers simultaneously can result in UAV 400 increasing ordecreasing its altitude, respectively.

Many variations on the illustrated fixed-wing aerial vehicle arepossible. Although FIGS. 4A and 4B illustrate one wing assembly 402, twoboom assemblies 410, two horizontal propulsion units 406, and sixvertical propulsion units 412 per boom assembly 410, it should beappreciated that other variants of UAV 400 may be implemented with moreor less of these components.

It should be understood that references herein to an “unmanned” aerialvehicle or UAV can apply equally to autonomous and semi-autonomousaerial vehicles. In a fully autonomous implementation, all functionalityof the aerial vehicle is automated; e.g., pre-programmed or controlledvia real-time computer functionality that responds to input from varioussensors and/or pre-determined information. In a semi-autonomousimplementation, some functions of an aerial vehicle may be controlled bya human operator, while other functions are carried out autonomously.Further, in some embodiments, a UAV may be configured to allow a remoteoperator to take over functions that can otherwise be controlledautonomously by the UAV. Yet further, a given type of function may becontrolled remotely at one level of abstraction and performedautonomously at another level of abstraction. For example, a remoteoperator may control high level navigation decisions for a UAV, such asspecifying that the UAV should travel from one location to another(e.g., from a warehouse in a suburban area to a delivery address in anearby city), while the UAV's navigation system autonomously controlsmore fine-grained navigation decisions, such as the specific route totake between the two locations, specific flight controls to achieve theroute and avoid obstacles while navigating the route, and so on.

FIG. 5 is a flow chart illustrating a process 500 for using adhocgeo-fiducials (e.g., geo-fiducials xx0-xx9) on geo-fiducial mat 110 tonavigate a takeoff, in accordance with an embodiment of the disclosure.The order in which some or all of the process blocks appear in process500 should not be deemed limiting. Rather, one of ordinary skill in theart having the benefit of the present disclosure will understand thatsome of the process blocks may be executed in a variety of orders notillustrated, or even in parallel.

A process block 505, UAV 105 receives mission data for a new missionfrom an operations server (aka nest manager). The mission data includesthe pad identification (e.g., 9 xx) of the mission home or landing padfrom where UAV 105 will commence its mission. The landing pad may alsoserve as a charging pad that charges the on-board battery of UAV 105.The mission data also includes location information of survey point 205.

Upon initialization, the controller of UAV 105 reviews the mission data,including the first segment 235 of the pad identification. If the firstsegment 235 has a value (e.g., 9) indicating that the landing pad isassociated with a geo-fiducial mat 110, then the controller willrecognize that the landing pad is associated with a geo-fiducial mat 110having multiple adhoc geo-fiducials (e.g., xx0-xx9) (process block 505).

In a process block 515, the locations of each adhoc geo-fiducial iscomputed based upon the location information received for survey point205 and the unique directional and offset positions specified for eachof the geo-fiducials. The specified directional and offset positions maybe preprogrammed values within the controller.

In a process block 520, the computed locations for each adhocgeo-fiducial xx0-xx9 are populated into a geo-fiducial map stored withinUAV 105. The geo-fiducial map is referenced by the controller of UAV 105for identifying geo-fiducials, determining their location, and thenself-triangulating therefrom. FIG. 6 illustrates an example geo-fiducialmap 600 that includes entries 601 for standard preprogrammedgeo-fiducials and entries 602 for adhoc geo-fiducials that may be addedinto the geo-fiducial map 600 on-the-fly. Geo-fiducial map 600 is merelydemonstrative, but the illustrated example includes columns for a padID, a fiducial marker (or code), an associated fiducial marker image, alatitude, a longitude, an altitude, a heading, and a zip code. Not allillustrated columns may be necessary in all embodiments, andfurthermore, other columns may be added.

After the latitude and longitude locations for the adhoc geo-fiducialsare calculated and populated into geo-fiducial map 600, then the missioncan commence in a decision block 525. In a process block 530, UAV 105rises to a takeoff waypoint above geo-fiducial mat 110. The takeoffwaypoint may be approximately 1 m above geo-fiducial mat 110. Thetakeoff waypoint may be considered as a validation waypoint. At thetakeoff waypoint, the optical navigation system of UAV 105 triangulatesits current position based upon one or more adhoc geo-fiducials xx0-xx9(process block 535). The optically triangulated position is comparedagainst a GPS sensed position, and if it validates within an acceptablemargin of error (decision block 540), then UAV 105 proceeds with itsmission (process block 545). If the optically triangulated position doesnot agree with the GPS position within an acceptable margin of error(decision block 540), then the mission is aborted and UAV 105 lands backon the landing pad (process block 550). In other words, thegeo-fiducials can be used by UAV 105 to validate the correct operationof its GPS sensor.

The processes explained above are described in terms of computersoftware and hardware. The techniques described may constitutemachine-executable instructions embodied within a tangible ornon-transitory machine (e.g., computer) readable storage medium, thatwhen executed by a machine will cause the machine to perform theoperations described. Additionally, the processes may be embodied withinhardware, such as an application specific integrated circuit (“ASIC”) orotherwise.

A tangible machine-readable storage medium includes any mechanism thatprovides (i.e., stores) information in a non-transitory form accessibleby a machine (e.g., a computer, network device, personal digitalassistant, manufacturing tool, any device with a set of one or moreprocessors, etc.). For example, a machine-readable storage mediumincludes recordable/non-recordable media (e.g., read only memory (ROM),random access memory (RAM), magnetic disk storage media, optical storagemedia, flash memory devices, etc.).

The above description of illustrated embodiments of the invention,including what is described in the Abstract, is not intended to beexhaustive or to limit the invention to the precise forms disclosed.While specific embodiments of, and examples for, the invention aredescribed herein for illustrative purposes, various modifications arepossible within the scope of the invention, as those skilled in therelevant art will recognize.

These modifications can be made to the invention in light of the abovedetailed description. The terms used in the following claims should notbe construed to limit the invention to the specific embodimentsdisclosed in the specification. Rather, the scope of the invention is tobe determined entirely by the following claims, which are to beconstrued in accordance with established doctrines of claiminterpretation.

What is claimed is:
 1. An apparatus for visual navigation of an unmannedaerial vehicle (UAV), the apparatus comprising: a geo-fiducial matincluding: a landing pad region that provides a location for aligningwith a landing pad of the UAV; and a survey point indicated on thegeo-fiducial mat; and a plurality of geo-fiducials disposed in or aboutthe landing pad region and each specified for a unique directional andoffset position relative to the survey point, wherein the geo-fiducialseach includes a two-dimensional (2D) pattern that visually conveys analphanumerical code, wherein the 2D pattern has a shape from which anoptical navigation system of the UAV can visually triangulate a positionof the UAV.
 2. The apparatus of claim 1, wherein the geo-fiducialscomprise at least three geo-fiducials that each convey a differentalphanumerical code and are disposed at three different corners or alongthree different sides of the landing pad region.
 3. The apparatus ofclaim 1, wherein the geo-fiducials comprise: first geo-fiducials havinga first size that are configured to be disposed on or attached to thelanding pad.
 4. The apparatus of claim 3, wherein the geo-fiducialsfurther comprise: second geo-fiducials having a second size, larger thanthe first size, the second geo-fiducials positioned further from acenter of the landing pad region than the first geo-fiducials.
 5. Theapparatus of claim 4, wherein the geo-fiducials further comprise: thirdgeo-fiducials having a third size, larger than the first and secondsizes, the third geo-fiducials positioned further from the center of thelanding pad region than the first and second geo-fiducials.
 6. Theapparatus of claim 4, wherein the landing pad region comprises arectangular shaped region, wherein the first geo-fiducials are disposedproximate to corners of the landing pad region, and wherein the secondgeo-fiducials are substantially centered along sides of the landing padregion.
 7. The apparatus of claim 4, wherein the second geo-fiducialsare integrated into the geo-fiducial mat while the first geo-fiducialsare configured to be physically distinct and separate from thegeo-fiducial mat for adhering to or otherwise disposing on the landingpad of the UAV.
 8. The apparatus of claim 1, wherein the geo-fiducialmat further includes: a directional marker disposed on the geo-fiducialmat for aligning the geo-fiducial mat with a predetermined directionsuch that positions of the geo-fiducials are determinable based uponlocation information of the survey point and the unique directional andoffset position specified for each of the geo-fiducials.
 9. Theapparatus of claim 1, wherein the geo-fiducial mat further includes:alignment markings disposed on the geo-fiducial mat for indicating thelanding pad region and aiding alignment of the landing pad to thelanding pad region.
 10. The apparatus of claim 1, wherein thealphanumerical code conveyed by each of the geo-fiducials shares acommon first portion that is associated with a pad identification of thelanding pad and a different second portion that individuallydistinguishes each of the geo-fiducials of the geo-fiducial mat fromeach other.
 11. The apparatus of claim 10, wherein the padidentification includes: a first segment having a value indicating thatthe geo-fiducials are not individually surveyed, but rather locations ofthe geo-fiducials are computable based at least in part upon locationinformation of the survey point; and a second segment that matches thecommon first portion of the alphanumerical code of each of thegeo-fiducials.
 12. The apparatus of claim 1, wherein the geo-fiducialmat comprises a flexible substrate material that is amenable to rollingor folding.
 13. The apparatus of claim 1, wherein the geo-fiducial matcomprises puzzle sections that are separable.
 14. A system fornavigating an unmanned aerial vehicle (UAV) during landing or takeoff,the system comprising: a charging pad for charging the UAV; ageo-fiducial mat including: a landing pad region that provides alocation for aligning the charging pad with the geo-fiducial mat; and asurvey point indicated on the geo-fiducial mat; and a plurality ofgeo-fiducials disposed in or about the charging pad region and eachspecified for a unique directional and offset position relative to thesurvey point, wherein the geo-fiducials each includes a two-dimensional(2D) pattern that visually conveys an alphanumerical code different fromeach other, wherein the 2D pattern has a shape from which an opticalnavigation system of the UAV can visually triangulate a position of theUAV.
 15. The system of claim 14, wherein the geo-fiducials comprise:first geo-fiducials having a first size that are configured to bedisposed on or attached to the charging pad.
 16. The system of claim 14,wherein the geo-fiducials comprise: first geo-fiducials having a firstsize; second geo-fiducials having a second size, larger than the firstsize, the second geo-fiducials positioned further from a center of thelanding pad region than the first geo-fiducials; and third geo-fiducialshaving a third size, larger than the first and second sizes, the thirdgeo-fiducials positioned further from the center of the landing padregion than the first and second geo-fiducials.
 17. The system of claim16, wherein the landing pad region comprises a rectangular shapedregion, wherein the first geo-fiducials are disposed proximate tocorners of the landing pad region, and wherein the second and thirdgeo-fiducials are substantially centered along sides of the landing padregion.
 18. The system of claim 16, wherein the second and thirdgeo-fiducials are integrated into the geo-fiducial mat while the firstgeo-fiducials are configured to be physically distinct and separate fromthe geo-fiducial mat for adhering to or otherwise disposing on thecharging pad of the UAV.
 19. The system of claim 14, wherein thegeo-fiducial mat further includes: a directional marker disposed on thegeo-fiducial mat for aligning the geo-fiducial mat with a predetermineddirection such that positions of the geo-fiducials are determinablebased upon location information of the survey point and the uniquedirectional and offset position specified for each of the geo-fiducials;and alignment markings disposed on the geo-fiducial mat for indicatingthe landing pad region and aiding alignment of the charging pad to thelanding pad region.
 20. The system of claim 14, wherein thealphanumerical code conveyed by each of the geo-fiducials shares acommon first portion that is associated with a pad identification of thelanding pad and a different second portion that individuallydistinguishes each of the geo-fiducials of the geo-fiducial mat fromeach other.
 21. The system of claim 20, further comprising the UAV,wherein the UAV includes a controller coupled to memory storinginstructions that when executed by the controller cause the UAV toperform operations comprising: identifying a first segment of the padidentification as indicating that the charging pad has multiplegeo-fiducials associated with the charging pad that are not individuallysurveyed; computing locations for the geo-fiducials based at least inpart upon location information of the survey point received by the UAVand the unique directional and offset position specified for each of thegeo-fiducials; and populating a geo-fiducial map stored within the UAVwith the locations for the geo-fiducials.
 22. The system of claim 14,further comprising the UAV, wherein the UAV includes a controllercoupled to memory storing instructions that when executed by thecontroller cause the UAV to perform operations comprising: flying theUAV to a takeoff way point above the geo-fiducial mat; visuallytriangulating the position of the UAV with the optical navigation systembased upon one or more of the geo-fiducials; and validating correctoperation of a global positioning system (GPS) sensor at the takeoffwaypoint based upon the position that is visually triangulated.